Turbofan as turbine engine

ABSTRACT

In a turbofan gas turbine engine, a fan shaft is rotatably mounted and radially supported by a bearing in a bearing support structure-supported from a fixed engine structure by radially frangible bolts and radially extending spokes. The radially inner ends of the radially extending spokes are mounted on a common member that engages the bearing support structure. The radially outer ends of the radially extending spokes are mounted on fixed structure of the engine located radially outwardly of the bearing support structure. The radially extending spokes are held in tension and include a super elastic material to exert a radially inward restoring force on the bearing support structure, subsequent to any radial excursion of at least part of the fan shaft relative to an engine rotational axis (X) following any fracture of the frangible bolts.

CROSS-REFERENCE TO RELATED APPLICATION

This application is a continuation application of U.S. Ser. No.11/938,980 filed Nov. 13, 2007, which is hereby incorporated byreference in its entirety.

FIELD OF THE INVENTION

The present invention relates to turbofan gas turbine engines, generallyand in particular, to a turbofan gas turbine engine with a fan shaftfrangible connection.

BACKGROUND OF THE INVENTION

Turbofan gas turbine engines are used for powering aircraft and comprisea relatively large diameter fan, which is driven by a core engine. Thefan is vulnerable to damage as a result of foreign objects entering theturbofan gas turbine engine. In most cases, the fan is sufficientlyrobust to withstand the effects of such foreign object ingestion withoutsuffering major damage and is able to continue operating, although,perhaps, at reduced efficiency.

On very rare occasions, the fan may be damaged to such an extent thatparts of one or more of the fan blades that make up the fan are lost.This usually necessitates shutting down of the turbofan gas turbineengine involved to minimise the hazard to the aircraft carrying it.However, the imbalance in the fan created by the fan blade lossinitially generates extremely high loads, which must, at leastpartially, be absorbed as the gas turbine engine is allowed to run-downto windmilling speed. Windmilling speed is the speed at which the gasturbine engine rotates in a non-operative condition as a result of itsmotion through the atmosphere.

The transients following the fan blade loss produce massive loads anddistortion of the bearing housing for the fan bearing and also insurrounding structure.

One way in which the fan imbalance load absorption may be achieved is toensure that the relevant engine structures are sufficiently strong totolerate the very high loads involved.

However, this results in a heavily reinforced structure both in theengine and aircraft, which results in an increase in weight of theengine and aircraft.

Other ways in which the fan imbalance load absorption may be achieved isto provide energy absorbing links and deforming housings.

Again, this results in an increase in weight of the engine and aircraftand the movement of the energy absorbing links or deforming housingsresults in permanent deformation of the structure and does not give astiff structure to control shaft/rotor dynamics during windmilling.

SUMMARY OF THE INVENTION

Accordingly, the present invention seeks to provide a novel turbofan gasturbine engine, which reduces, preferably, overcomes the above-mentionedproblem.

Accordingly, the present invention provides a turbofan gas turbineengine comprising a fan mounted on a fan shaft, the fan shaft beingnormally coaxial with said engine rotational axis, the fan shaft beingrotatably mounted and radially supported by a bearing in a bearingsupport structure, the bearing support structure being supported from afixed structure of the engine by at least one member, a first end of theat least one member engaging the bearing support structure and a secondend of the member being mounted on the fixed structure, the at least onemember comprising a super elastic material, the at least one memberexerting a radially inward restoring force on the bearing supportstructure, and hence the fan shaft, subsequent to any radial excursionof at least part of the fan shaft relative to the rotational axis of theengine.

Preferably, the at least one member comprising at least one generallyradially extending member, the radially inner end of the at least oneradially extending member being mounted on a common member, the commonmember engaging the bearing support structure, the radially outer end ofthe at least one radially extending member being mounted on fixedstructure of the engine located radially outwardly of the bearingsupport structure, the at least one radially extending member being heldin tension, the at least one radially extending member exerting aradially inward restoring force on the bearing support structure, andhence the fan shaft, subsequent to any radial excursion of at least partof the fan shaft relative to the rotational axis of the engine.

Preferably, the bearing support structure being supported from fixedstructure of the engine by a radially frangible connection means, the atleast one radially extending member exerting a radially inward restoringforce on the bearing support structure, and hence the fan shaft,subsequent to any radial excursion of at least part of the fan shaftrelative to the rotational axis of the engine following any fracture ofthe frangible connection means.

Preferably, the at least one radially extending member comprises aplurality of generally radially extending spokes, the radially innerends of the radially extending spokes being mounted on a common member,the common member engages the bearing support structure, the radiallyouter ends of the radially extending spokes being mounted on fixedstructure of the engine located radially outwardly of the bearingsupport structure, the radially extending spokes being held in tension.

Preferably, the radially inner ends of the radially extending spokes aredovetail shaped in cross-section and engage dovetail shaped slots in thecommon member.

Preferably, the radially outer ends of the radially extending spokes aredovetail shaped in cross-section and engage dovetail shaped slots in thefixed structure.

Alternatively, the at least one radially extending member comprises atleast one disc or at least one cone.

Alternatively, the at least one member comprising at least one generallyaxially extending member, a first axial end of the at least one axiallyextending member engaging the bearing support structure, a second axialend of the at least one axially extending member being mounted on fixedstructure of the engine, the at least one axially extending memberexerting a radially inward restoring force on the bearing supportstructure, and hence the fan shaft, subsequent to any radial excursionof at least part of the fan shaft relative to the rotational axis of theengine.

The at least one axially extending member may comprise at least one drumor at least one beam.

Preferably, the super elastic material comprises a super elastic metal.

Preferably, the super elastic metal comprises a shape memory metal.

Preferably, the shape memory metal comprises Ni—Ti alloy.

Alternatively, the super elastic metal comprises Ti—Nb alloy.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 shows a turbofan gas turbine engine according to the presentinvention.

FIG. 2 shows an enlarged cross-sectional view of a portion of a fanrotor and a bearing support structure according to the presentinvention.

FIG. 3 shows a view in the direction of arrow A of the bearing supportstructure shown in FIG. 2.

FIG. 4 is a graph of stress against strain for a super elastic material.

FIG. 5 shows an alternative enlarged cross-sectional view of a portionof a further fan rotor and a bearing support structure according to thepresent invention.

FIG. 6 shows an alternative schematic enlarged cross-sectional view of aportion of a further fan rotor and a bearing support structure accordingto the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

A turbofan gas turbine engine 10, as shown in FIG. 1, comprises in axialflow series an inlet 12, a fan section 14, a compressor section 16, acombustion section 18, a turbine section 20 and an exhaust 22. The fansection 14 comprises a fan, which includes a fan rotor 24 carrying aplurality of circumferentially spaced radially outwardly extending fanblades 26. The fan rotor 24 and fan blades 26 are surrounded by a fancasing 28 to define a fan duct 30. The fan casing 28 is supported from acore engine casing 32 by a plurality of circumferentially spacedradially extending fan outlet guide vanes 34. The compressor section 16comprises an intermediate-pressure compressor (not shown) and ahigh-pressure compressor (not shown) or a high-pressure compressor (notshown). The turbine section 20 comprises a high-pressure turbine (notshown), an intermediate-pressure turbine (not shown) and a low-pressureturbine (not shown) or a high-pressure turbine (not shown) and alow-pressure turbine (not shown). The low-pressure turbine is arrangedto drive the fan via a fan shaft 36, the intermediate-pressure turbineis arranged to drive the intermediate-pressure compressor via a shaft(not shown) and the high-pressure turbine is arranged to drive thehigh-pressure compressor via a shaft (not shown).

The fan is supported from fixed structure of the turbofan gas turbineengine 10 as is shown more clearly in FIGS. 2 and 3. The fan, the fanrotor 24 is mounted on the fan shaft 36 and the fan shaft 36 is normallycoaxial with the rotational axis X of the turbofan gas turbine engine10.

The fan shaft 36 is rotatably mounted and radially supported by a numberof roller bearings spaced axially along the fan shaft 36. A rollerbearing 38 axially adjacent the fan rotor 24 is supported in a bearingsupport structure 40. The roller bearing 38 comprises a radially innerrace 42 on a radially outer surface of the fan shaft 36, a radiallyouter race 44 and a plurality of roller elements 46 between the innerrace 42 and the outer race 44. The radially outer race 44 is supportedby the bearing support structure 40.

The bearing support structure 40 is supported from fixed structure 42 ofthe turbofan gas turbine engine 10 by a radially frangible connection,for example a plurality of frangible axially extending bolts 48. Thefixed structure 42 comprises two annular panels 50 and 52, which areaxially spaced at their radially inner ends by a cylindrical member 54and the radially outer ends of the annular panels 50 and 52 areconnected by an annular member to define the radially inner platforms 56of a set of stator vanes 58. The stator vanes 58 are secured at theirradially outer ends to the core engine casing 32.

In addition, a plurality of equally circumferentially spaced generallyradially extending spokes 60 are provided, the radially inner ends 62 ofthe radially extending spokes 60 are mounted on a common member 64 andthe common member 64 engages the radially outer periphery of the bearingsupport structure 40. The radially outer ends 66 of the radiallyextending spokes 60 are mounted on the fixed structure 42 of theturbofan gas turbine engine 10 located radially outwardly of the bearingsupport structure 40. The radially extending spokes 60 are held intension and the radially extending spokes 60 comprise a super elasticmaterial. The super elastic material comprises a super elastic metal,for example a shape memory metal e.g. Ni—Ti shape memory metal or gummetal, e.g. a Ti—Nb alloy. Other suitable super elastic metals may beused.

The radially inner ends 62 of the radially extending spokes 60 aredovetail shaped in cross-section and engage dovetail shaped slots 68 inthe common member 64. The radially outer ends 66 of the radiallyextending spokes 60 are dovetail shaped in cross-section and engagedovetail shaped slots 70 in a ring member 72 forming part of the fixedstructure 42.

The generally radially extending spokes 60 as shown in FIGS. 2 and 3 arearranged at an angle to a plane arranged perpendicular to the rotationalaxis X of the turbofan gas turbine engine 10 and the radially outer endsof the spokes 60 are arranged axially downstream from the radially innerends of the spokes. The generally radially extending spokes 60 arearranged in a plane containing the rotational axis X of the turbofan gasturbine engine 10.

In the event of the fan suffering damage to one or more of the fanblades 26, which places the fan significantly out of balance,considerable radial loads are transmitted from the fan shaft 36 to thebearing support structure 40 via the roller bearing 38. These loads arethen transmitted to the fixed structure 42 via the frangible bolts 48.However, in order to protect the core engine from being seriouslydamaged by the radial loads, the frangible bolts 48 are designed to befrangible in such a manner that they fracture in shear when subjected toloads above a predetermined load. If this occurs, the upstream end ofthe fan shaft 36 no longer has radial support and so it proceeds toorbit around the rotational axis X of the turbofan gas turbine engine10.

However, the radially extending spokes 60 via the common member 64 exerta radially inward restoring force on the bearing support structure 40,and hence on the fan shaft 36, subsequent to any radial excursion of atleast part of the fan shaft 36 relative to the rotational axis X of theturbofan gas turbine engine following any fracture of the frangiblebolts 48. The radially extending spokes 60 have high strain and energyabsorption and are placed in tension between their radially inner ends62 and radially outer ends 66. The radially extending spokes 60 havevery large recoverable strains, about 10%, and provide high-energyabsorption and have a non-linear stress-strain curve, as shown in FIG.4, which minimises permanent deformation and retains stiffness at lowstrain levels. The radially extending spokes 60 have low stiffness athigh strain levels for reduction of damage during a fan blade off event,they have high energy absorption, they are lightweight and compact andhave high stiffness following a fan blade off event to provide goodcontrol of the fan during windmilling. Region A on the graph is theregion corresponding to normal operation of the radially extendingspokes 60, region B on the graph is the region corresponding tooperation of the spokes 60 during fan windmilling and region C on thegraph corresponds to operation of the spokes 60 during out of balancefollowing a fan blade off event.

Thus, the present invention provides a mounting for a fan of a gasturbine engine incorporating a super elastic material, which provides astiff structure during normal operation, limits loads to maintain thestructure during a fan blade off event, provides high energy dissipationand returns to its original shape after the fan blade off event.

Although the present invention has been described with reference togenerally radially extending spokes, the spokes may be arranged suchthat the outer ends of the generally radially extending spokes arespaced circumferentially from the radially inner ends of the spokes, andmay be arranged in a manner similar to the spokes of a bicycle wheel.

Although the present invention has been described with reference to aplurality of generally radially extending spokes it may be possible toprovide at least one generally radially extending member, the radiallyinner end of the at least one radially extending member being mounted ona common member, the common member engaging the bearing supportstructure, the radially outer end of the at least one radially extendingmember being mounted on fixed structure of the engine located radiallyoutwardly of the bearing support structure, the at least one radiallyextending member being held in tension and the at least one radiallyextending member comprising a super elastic material.

The generally radially extending member may comprise at least one discor at least one cone.

In an alternative arrangement the fan shaft 36 is supported from fixedstructure of the turbofan gas turbine engine 10, as shown more clearlyin FIG. 5. This arrangement is similar to FIGS. 2 and 3, but without thefrangible connection, frangible bolts, and the fixed support structurecomprising two annular panels secured to a cylindrical member at theirradially inner ends. In this instance the radially extending spokes 60alone provide the support between the bearing housing 40 and the statorvanes 58.

Although the present invention has been described with reference to atleast one generally radially extending member, it may also be possibleto provide at least one axially extending member instead of a radiallyextending member, e.g. a drum or a plurality of axially extending beams.

In an alternative arrangement, the fan shaft 36 is supported from fixedstructure of the turbofan gas turbine engine 10 as is shown more clearlyin FIG. 6. The fan, the fan rotor 24 is mounted on the fan shaft 36 andthe fan shaft 36 is normally coaxial with the rotational axis X of theturbofan gas turbine engine 10. In addition an axially extending drum 80is provided, the axially upstream end 62 of the drum 80 engages theradially outer periphery of the bearing support structure 40. Theaxially downstream end of the drum 80 is mounted on the fixed structure42 of the turbofan gas turbine engine 10 located radially outwardly ofthe bearing support structure 40, by the annular panel 82 etc. The drum80 comprises a super elastic material. The super elastic materialcomprises a super elastic metal, for example a shape memory metal e.g.Ni—Ti shape memory alloy or gum metal e.g. Ti—Nb alloy. Other suitablesuper elastic metals may be used, e.g. Ti—Ni—Cu, Ti—Ni—Nb, Ti—Ni—Hf,Cu—Zn—Al, Cu—Al—Ni etc.

Similarly, although the invention has been shown and described withrespect to a best mode embodiment thereof, it should be understood bythose skilled in the art that various other changes, omissions andadditions thereto may be made therein without departing from the spiritand scope of the invention.

What is claimed is:
 1. A turbofan gas turbine engine comprising a fanmounted on a fan shaft, the fan shaft being normally coaxial with anengine rotational axis, the fan shaft being rotatably mounted andradially supported by a bearing in a bearing support structure, thebearing support structure being supported from a fixed structure of theengine by at least one member, a first end of the at least one memberengaging the bearing support structure and a second end of the memberbeing mounted on the fixed structure, the at least one member comprisinga super elastic material, the at least one member exerting a radiallyinward restoring force on the bearing support structure, and hence thefan shaft, subsequent to a radial excursion of at least part of the fanshaft relative to the rotational axis of the engine.
 2. A turbofan gasturbine engine as claimed in claim 1 wherein the at least one memberfurther comprises at least one generally radially extending member, aradially inner end of the at least one radially extending member beingmounted on a common member, the common member engaging the bearingsupport structure, the radially outer end of the at least one radiallyextending member being mounted on the fixed structure of the enginelocated radially outwardly of the bearing support structure, the atleast one radially extending member being held in tension, the at leastone radially extending member exerting a radially inward restoring forceon the bearing support structure, and hence the fan shaft, subsequent toany radial excursion of at least part of the fan shaft relative to therotational axis of the engine.
 3. A turbofan gas turbine engine asclaimed in claim 2 wherein the at least one radially extending memberfurther comprises a plurality of generally radially extending spokes,the radially inner ends of the radially extending spokes being mountedon a common member, the common member engages the bearing supportstructure, the radially outer ends of the radially extending spokesbeing mounted on fixed structure of the engine located radiallyoutwardly of the bearing support structure, the radially extendingspokes being held in tension.
 4. A turbofan gas turbine engine asclaimed in claim 3 wherein the radially outer ends of the radiallyextending spokes are spaced circumferentially from the radially innerends of the radially extending spokes.
 5. A turbofan gas turbine engineas claimed in claim 3, wherein radial gaps are formed between theradially outer ends of the radially extending spokes and the radiallyouter ends of the corresponding slots in the fixed structure.
 6. Aturbofan gas turbine engine as claimed in claim 2 wherein the at leastone radially extending member is selected from the group consisting ofat least one disc and at least one cone.
 7. A turbofan gas turbineengine as claimed in claim 1 wherein the at least one member furthercomprises at least one generally axially extending member, a first axialend of the at least one axially extending member engaging the bearingsupport structure, a second axial end of the at least one axiallyextending member being mounted on the fixed structure of the engine, theat least one axially extending member exerting a radially inwardrestoring force on the bearing support structure, and hence the fanshaft, subsequent to any radial excursion of at least part of the fanshaft relative to the rotational axis of the engine.
 8. A turbofan gasturbine engine as claimed in claim 7 wherein the at least one axiallyextending member comprises at least one drum or at least one beam.
 9. Aturbofan gas turbine engine as claimed in claim 1 wherein the superelastic material comprises a super elastic metal.
 10. A turbofan gasturbine engine as claimed in claim 9 wherein the super elastic metalcomprises a shape memory metal.
 11. A turbofan gas turbine engine asclaimed in claim 10 wherein the shape memory metal comprises Ni—Tialloy.
 12. A turbofan gas turbine engine as claimed in claim 9 whereinthe super elastic metal comprises Ti—Nb alloy.
 13. A turbofan gasturbine engine as claimed in claim 9 wherein the super elastic metal isselected from the group consisting of Ti—Ni—Cu, Ti—Ni—Nb, Ti—Ni—Hf,Cu—Zn—Al and Cu—Al—Ni.